公开(公告)号：US20250043730A1

公开(公告)日：2025-02-06

申请号：US18919910

申请日：2024-10-18

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Lance L. Smith ,  Neal R. Herring ,  Christopher J. Hanlon

IPC: F02C7/32 ,  F02C7/141 ,  F02C7/18

Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.

公开(公告)号：US12196137B2

公开(公告)日：2025-01-14

申请号：US17345205

申请日：2021-06-11

Applicant: RTX Corporation

Inventor： Neil Terwilliger ,  Lance L. Smith ,  Neal R. Herring ,  Christopher J. Hanlon

IPC: F02C7/32 ,  F02C7/141 ,  F02C7/18

Abstract: A gas turbine engine includes a turbine section located at an engine central longitudinal axis, a combustor configured to drive rotation of the turbine with combustion products, and a compressor section coupled to the turbine section at the engine central longitudinal axis and driven by the turbine section. An auxiliary compressor is located fluidly between the compressor section and the combustor such that an airflow exiting the compressor section is directed toward the auxiliary compressor. The auxiliary compressor is driven independently from the compressor section and is configured to output the airflow toward the combustor.

公开(公告)号：US11781479B2

公开(公告)日：2023-10-10

申请号：US17313605

申请日：2021-05-06

Applicant: RTX Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis ,  Christopher J. Hanlon

IPC: F02C7/052

CPC classification number: F02C7/052 ,  F05D2220/32

Abstract: A gas turbine engine includes a core section including a compressor, a main combustor, and a main turbine. Combustion products from the main combustor drive rotation of the turbine and the compressor. A power turbine is fluidly connected to the main turbine and driven by exhaust from the main turbine. The gas turbine engine further includes a fan section having a fan rotor located fluidly upstream of the core section. The power turbine is operably connected to the fan rotor to drive rotation of the fan rotor via rotation of the power turbine. The gas turbine engine includes a bleed arrangement having one or more bleed passages configured to divert a bleed airflow from the compressor around the main combustor and main turbine, and reintroduce the bleed airflow into the power turbine.

公开(公告)号：US11840958B2

公开(公告)日：2023-12-12

申请号：US17393508

申请日：2021-08-04

Applicant: RTX Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Christopher J. Hanlon

IPC: F02C6/02 ,  F02C3/10 ,  F02C7/36 ,  F02C3/14 ,  F02C7/04 ,  F02K3/04

CPC classification number: F02C3/10 ,  F02C6/02 ,  F02C7/36 ,  F02C3/14 ,  F02C7/04 ,  F02K3/04

Abstract: A gas turbine engine includes a fan positioned at an engine central longitudinal axis, and a fan drive turbine located at the engine central longitudinal axis and configured to drive rotation of the fan. A gas generator is non-coaxial with the fan drive turbine and operably connected to the fan drive turbine such that exhaust from the gas generator drives rotation of the fan drive turbine. An auxiliary power core is located at the engine central longitudinal axis, and one or more bleed passages connect the gas generator and the auxiliary power core. The one or more bleed passages are configured to selectably combine a bleed airflow from the gas generator and an auxiliary core airflow at the auxiliary power core to direct the combined airflow to the fan drive turbine to increase output of the fan drive turbine.

公开(公告)号：US12134984B1

公开(公告)日：2024-11-05

申请号：US18512433

申请日：2023-11-17

Applicant: RTX CORPORATION

Inventor： Simon W. Evans ,  Christopher J. Hanlon

IPC: F02C7/143 ,  B64D33/08

Abstract: A propulsion system for an aircraft includes an intercooling system with a plurality of injectors for injecting an intercooling waterflow into a portion of a compressor passage. The plurality of injectors are spaced apart about the compressor passage and the injection of the intercooling water flow is varied between the plurality of injectors to influence flow that is communicated through the compressor passage.

公开(公告)号：US20250146441A1

公开(公告)日：2025-05-08

申请号：US18386381

申请日：2023-11-02

Applicant: RTX Corporation

Inventor： Jorn A. Glahn ,  Kimberly J. Liang ,  Christopher J. Hanlon

IPC: F02C7/18 ,  F04D17/10 ,  F04D25/06

Abstract: An electrically boosted cooling air system including a high pressure compressor; at least one cooling air supply line coupling the high pressure compressor with at least one of a high pressure turbine and a low pressure turbine; and an electrically powered centrifugal compressor fluidly coupled with the at least one cooling air supply line; wherein the electrically powered centrifugal compressor is configured to provide at least one of a pressure increase and a flow rate increase for cooling air supplied from the high pressure compressor.